21st Congress of International Council of the Aeronautical Sciences, Melbourne, Australia, 13-18 September, 1998
Paper ICAS-98-3.3.1

LUMINESCENT PAINT TECHNOLOGY FOR TEMPERATURE AND PRESSURE MEASUREMENTS IN A CRYOGENIC WIND TUNNEL

Asai K., Sullivan P.*
National Aerospace Laboratory, Japan; *School of Aeronautics and Astronautics, Purdue University, USA

Keywords: luminescent paint technology, temperature, pressure, measurement , cryogenic, wind tunnel

In recent experiments, we demonstrated the feasibility of using luminescent paints for temperature and pressure measurements in a cryogenic wind tunnel. This technique is based on the photo-physical processes known as thermal-and oxygen-quenching. Through these processes, the luminescent intensity of the paint emission can be related to temperature or pressure. Verification tests have been performed in NAL O.I-m Transonic Cryogenic Wind Tunnel. Using temperature-sensitive paints based on ruthenium complex and silicone polymer, boundary-layer transition on an airfoil model has been successfully detected from 90 to 150 Kelvin. Likewise, using pressure-sensitive coating based on ruthenium molecules and anodized porous alumina, surface pressure field including shock waves and flow separation has been clearly captured in cryogenic flow. As has been demonstrated by these experiments, the luminescent paint technology works in the adverse flow condition in a cryogenic wind tunnel. It would be possible to develop the cryogenic TSP and PSP systems that is much superior to that for ambient-temperature testing.

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